CA2325146A1 - System for controlling a unit of short-range surface-to-air missiles - Google Patents
System for controlling a unit of short-range surface-to-air missiles Download PDFInfo
- Publication number
- CA2325146A1 CA2325146A1 CA002325146A CA2325146A CA2325146A1 CA 2325146 A1 CA2325146 A1 CA 2325146A1 CA 002325146 A CA002325146 A CA 002325146A CA 2325146 A CA2325146 A CA 2325146A CA 2325146 A1 CA2325146 A1 CA 2325146A1
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- Prior art keywords
- tracking
- radar
- missile
- coordinates
- launch
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/66—Radar-tracking systems; Analogous systems
- G01S13/72—Radar-tracking systems; Analogous systems for two-dimensional tracking, e.g. combination of angle and range tracking, track-while-scan radar
- G01S13/723—Radar-tracking systems; Analogous systems for two-dimensional tracking, e.g. combination of angle and range tracking, track-while-scan radar by using numerical data
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/30—Command link guidance systems
- F41G7/301—Details
- F41G7/303—Sighting or tracking devices especially provided for simultaneous observation of the target and of the missile
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
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- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Radar Systems Or Details Thereof (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The present invention pertains to the field of radiolocation techniques and may be used in the control systems of anti-aircraft weapons. The control system of the present invention comprises the following members: detection means provided with an omnidirectional scanning radar; an IFF radar interrogator; means for tracking and precisely measuring the co-ordinates of the target and the missile; means for displaying information; a radio transponder; a calculator for calculating the moment when the target enters the shooting area; an angular misalignment calculator; a range and azimuthal tracking device; a control system for the beam of the tracking radar; a programmable search device; a system for tracking a plurality of objects according to four co-ordinates; a device for controlling the width of the directional characteristics of the tracking radar in the missile radio transponder; a missile radio beacon; a tracking radar of the missile radio beacon; a switch; and a device for recognising the type of the target and for adapting the operation modes of the missile control system.
Description
SYSTEM FOR CONTROr~ING A UNIT OF SHORT-RANGE SURFACE-TO-AIR MISSILES
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Said goal is to be attained as follows: a guidance system of a short-range army-used anti-aircraft missile unit, which is mounted on a single self-propelled carrier or in a conveyance container, is equipped with a means for partial control of the all-round looking radar antenna beams, having a phase-shift device and a receiving system of which radar is of the «n-channel» type; a device for the range and azimuth tracking basing on the information supplied from the all-round looking radar; a system for controlling the tracking radar beam, the antenna of which radar is implemented in the form of a phased array; a programmable search device; a system for simultaneous tracking basing on four coordinates (azimuth, elevation, range and Doppler frequency) of several objects by the tracking radar; a device for controlling the pattern width of the missile transponder's tracking radar; a missile beacon; a missile beacons' tracking radar; a switching means, a device for identifying the target class and adapting the modes of operation of the missiles control systems, including a signal spectral analysis unit, an evaluator for evaluating the pre-launch command information and the missile deviation angles after the vertical launch; a device for analysing the launch results; means for continuous functional monitoring of the combat hardware; and the missile computation control system is equipped with a second evaluator for evaluating the time a ~.5 target enters the launch area, the identifying interrogator i antenna pattern being deployed in azimuth with respect to the all-round looking radar antenna in the direction opposite to that of rotation of the latter.
Fig. 1 shows a functional diagram of the proposed guidance ~ system for a short-range anti-aircraft missile unit; said system comprising:
a means 1 for partial control of antenna beams, having a phase-shift device;
detection means 2 having an all-round looking radar;
35 range and azimuth tracking device 3;
radar-based identification interrogator 4;
Fig. 1 shows a functional diagram of the proposed guidance ~ system for a short-range anti-aircraft missile unit; said system comprising:
a means 1 for partial control of antenna beams, having a phase-shift device;
detection means 2 having an all-round looking radar;
35 range and azimuth tracking device 3;
radar-based identification interrogator 4;
second evaluator 5 for evaluating the time a target enters the launch area;
devices 6 for the missile pre-launch preparation and launch execution;
evaluator 7 for evaluating the time a target enters the launch area;
system 8 for controlling the antenna beam of means 10 for tracking and precision-measurement of the target and missile coordinates;
programmable search device 9;
system 11 for simultaneous tracking basing on four coordinates (azimuth, elevation, range and Doppler frequency) of several objects by a tracking radar of means 10;
device 12 for analysing the launch results;
device 13 for identifying the target class and adapting the modes of operation of the missile control systems, including a signal spectral analysis unit:
angular misalignment evaluator 14;
switching device 15;
evaluator 16 for evaluating the pre-launch command information and missile deviation angles after the vertical launch;
device 17 for controlling the pattern width of the tracking radar of missile interrogator 18 of means 10:
$ missile autopilot 19;
tracking radar 20 of missile beacon 21;
means 22 for information display;
device 23 for continuous functional monitoring of the combat devices.
The claimed arrangement functions as follows. A
transmitter of all-round looking radar 2 generates a sounding signal simultaneously upon several carrier frequencies. Owing to the presence of high-frequency phase-shift device 1 connected to emitters of the all-round looking radar 2 antenna, 35 the latter generates beams whose position in the elevation plane depends on a carrier frequency. Thus, the sounding signal generated upon several frequencies is emitted simultaneously in a number of directions according to the elevation.
This circumstance allows to sound the space by a radar simultaneously by a number of partial elevation lobes, which provides a simultaneous space surveillance, and finally results in a decrease of the time requ;~red to survey a predetermined surveillance space.
A receiver of the all-round looking radar is of the «n channel» type (as regards the number of elevation partials).
The radar information received by the n-channel receiver is supplied to a device for turning on a transmitter of identifying interrogator 4 for the automatic target identification. Coordinates of the detected targets, from output of the n-channel receiver of the all-round looking radar are supplied to device 3 for range and azimuth tracking.
The electrical axis of the radar-based identification interrogator 4 is deviated in azimuth from the that of the all-round looking radar 2 antenna in the direction opposite to that of rotation of the antenna, by an angle not less than an half of the beam width of the radar-based identification interrogator 4 antenna, in the azimuth plane.
Generation of said command to turn on the radar-based identification interrogator commences from the moment a target is detected. Duration of this command equals the time period during which the radar-based identification interrogator 4 intersects the detected target in azimuth.
By virtue of all the above-discussed steps, each detected target is identified automatically «en route», i.e. a target is identified in the same surveillance cycle wherein such target is detected.
The radar-based detection information from output of the n-channel receiver of the all-round looking radar of detection means 2 and the radar-based identification information from output of the radar-based identification interrogator 4 are supplied to range and azimuth tracking device 3.
Device 3, using a discrete flow of the input information on the targets' coordinates which are provided as the surveillance rate proceeds, performs the continuous tracking of such targets in their range and azimuth, and generates the following target-indicating data for system 11 for simultaneous tracking basing on four coordinates of several objects:
devices 6 for the missile pre-launch preparation and launch execution;
evaluator 7 for evaluating the time a target enters the launch area;
system 8 for controlling the antenna beam of means 10 for tracking and precision-measurement of the target and missile coordinates;
programmable search device 9;
system 11 for simultaneous tracking basing on four coordinates (azimuth, elevation, range and Doppler frequency) of several objects by a tracking radar of means 10;
device 12 for analysing the launch results;
device 13 for identifying the target class and adapting the modes of operation of the missile control systems, including a signal spectral analysis unit:
angular misalignment evaluator 14;
switching device 15;
evaluator 16 for evaluating the pre-launch command information and missile deviation angles after the vertical launch;
device 17 for controlling the pattern width of the tracking radar of missile interrogator 18 of means 10:
$ missile autopilot 19;
tracking radar 20 of missile beacon 21;
means 22 for information display;
device 23 for continuous functional monitoring of the combat devices.
The claimed arrangement functions as follows. A
transmitter of all-round looking radar 2 generates a sounding signal simultaneously upon several carrier frequencies. Owing to the presence of high-frequency phase-shift device 1 connected to emitters of the all-round looking radar 2 antenna, 35 the latter generates beams whose position in the elevation plane depends on a carrier frequency. Thus, the sounding signal generated upon several frequencies is emitted simultaneously in a number of directions according to the elevation.
This circumstance allows to sound the space by a radar simultaneously by a number of partial elevation lobes, which provides a simultaneous space surveillance, and finally results in a decrease of the time requ;~red to survey a predetermined surveillance space.
A receiver of the all-round looking radar is of the «n channel» type (as regards the number of elevation partials).
The radar information received by the n-channel receiver is supplied to a device for turning on a transmitter of identifying interrogator 4 for the automatic target identification. Coordinates of the detected targets, from output of the n-channel receiver of the all-round looking radar are supplied to device 3 for range and azimuth tracking.
The electrical axis of the radar-based identification interrogator 4 is deviated in azimuth from the that of the all-round looking radar 2 antenna in the direction opposite to that of rotation of the antenna, by an angle not less than an half of the beam width of the radar-based identification interrogator 4 antenna, in the azimuth plane.
Generation of said command to turn on the radar-based identification interrogator commences from the moment a target is detected. Duration of this command equals the time period during which the radar-based identification interrogator 4 intersects the detected target in azimuth.
By virtue of all the above-discussed steps, each detected target is identified automatically «en route», i.e. a target is identified in the same surveillance cycle wherein such target is detected.
The radar-based detection information from output of the n-channel receiver of the all-round looking radar of detection means 2 and the radar-based identification information from output of the radar-based identification interrogator 4 are supplied to range and azimuth tracking device 3.
Device 3, using a discrete flow of the input information on the targets' coordinates which are provided as the surveillance rate proceeds, performs the continuous tracking of such targets in their range and azimuth, and generates the following target-indicating data for system 11 for simultaneous tracking basing on four coordinates of several objects:
5 smoothed target coordinates and derivatives of the target smoothed coordinates. Thereby, owing to the circumstance that the identification information is provided, the tracking is executed only over the «enemy» target coordinates.
Second evaluator 5 for evaluating the time a target enters the lasnch area according to the data obtained from device 3, estimates the time a target enters the launch area and estimates the time when devices 6 for the missile pre-launch preparation and launch execution shall be turned on, which .1 devices send the preparation and launch commands to a missile.
Thus, these estimates are provided as early as before the information on the target coodinates is obtained from output of means 10 for tracking and precision-measurement of the target and missile coordinates.
Said target data (the target coordinates and their derivatives) from output of the range and azimuth tracking device 3 are supplied to the system 11 for simultaneous tracking basing on four coordinates (azimuth, elevation, range and Doppler frequency) of several objects by radar of means 10 for tracking and precision-measurement of target coordinates, ~5 and processed by said means.
The antenna of the radar of means 10 is implemented in the form of a phased array (PA). The tracking is carried out in the time-division mode by consecutive referrals of the PA beam to targets and missiles.
3~ To proceed to the target lock-on by the radar of means 10, without the operator's attendance, programmable radar-based search device 9 arranges for the target search within the space area determined by the target-indicating data errors committed by the all-round looking radar of means 2. Device 9 35 consecutively generates coordinates of the PA angular positions, which are delivered to system 8 for controlling the PA beam. As a result of operation of the controlling system 8, the PA beam is directed to a pre-determined angular direction.
Consecutive positions of the PA pattern can be a field raster, for example.
Radar of means 10, in each angular direction, emits a sounding signal. The echo signal, received by the radar receiver of means 10, is used to detect targets and determine their coordinates. Therefor, used is the joint processing of information obtained from a number of angular directions and the range and speed increments.
The joint processing can be done, for example, on the basis of evaluation of the energy centre (gravity centre of a spatial figure). The so obtained amended targets' coordinates are supplied from the means 10 radar to tracking systems 11 for simultaneous tracking basing on four coordinates. Owing to a sufficient accuracy of determining said target coordinates, the simultaneous four-coordinate tracking systems 11 from this moment on proceed to the continuous automatic target tracking.
Such arrangements for the target search using the means 10 tracking radar within the limit of the target-indicating errors 2~ committed by the all-round looking radar of detection means 2 allow to proceed to the lock-on by the tracking means 10 radar in a short time without the operator's attendance.
The target coordinates from output of the simultaneous tracking system 11 are delivered to input of evaluator 7 for ~5 evaluating the time a target enters the launch area, which s evaluator from that moment on evaluates the amended time a target will enter the launch area and performs the exact estimate of the time the missile pre-launch and launch execution devices 6 shall be turned on.
30 Signals from output of the tracking means 10 radar receiver, as well as the locked-on targets coordinates and their derivatives from the simultaneous tracking systems 11 are supplied to input of identification device 13. The identification device determines the features that characterise 35 the target being tracked. The following can be used as such features, for example: spectral composition of the signal reflected from a target, a signal strength and target movement parameters, such as the velocity vector module and tracked target altitude. Basing on the logical analysis of combinations of the determined features, a decision is made on the target's association with one of the classes. The identification result is given to a unit for generating the control commands of the tracking means 10 transponder 18 to match the time and mode of the missile combat portion explosion with the radio-controlled explosive device activation time, which allows to improve probability that a target will be destroyed.
In the pre-launch period, the target coordinates from output of tracking system 11 are supplied to evaluator 16 for evaluating the pre-launch command information and deviation angles. The signals generated by evaluator 16 are continuously delivered to autopilot 19. The deviation angle signals generated at the launch moment are stored by a storage member of autopilot 19, and at the autonomous flight stage the missile hull is steered by autopilot 19 and the controls such that direction of the longitudinal axis thereof will be proximate to the missile flight kinematic path tangent. When the missile position at the moment the radio guidance commences is such, a short range required to bring a missile to the kinematic path and a short range to the nearest destruction area boundary are ensured. Missiles are launched vertically. Use of the vertical launch allows to increase the carried missiles store owing to ~$ their positioning at the rotation centre, which permits to a decrease the inertia moment and the azimuth drive capacity.
Immediately after the launch, tracking radar 20 of missile beacon 21 performs acquisition and tracking of missile beacon 21 according to the angular coordinates. Employment of beacon 21 in a missile and providing the tracking radar 20 system with said beacon ensures the missile acquisition and tracking at the stage of its autonomous flight when the same is still outside the limits of the PA beam scanning sector of tracking means 10 radar of transponder 18.
At the same time, the phased array of the radar of means 10 forms a wide pattern for transmitting the interrogating signals and receiving the transponder 18 response signals.
g Evaluator 14 for evaluating the angular misalignments compares the missile angular coordinates, as measured by tracking radar 20 of_ missile beacon 21, and the PA scanning sector boundaries.
Angular misalignments evaluator 14 provides the target-indicating data to the means 10 transponder tracking radar from tracking radar 20 of beacon 21 and performs the switching, using switching means 15 of said radar of means 10 to implement lock-on of transponder 18 according to the angular coordinates when a missile enters the phased array sector. Switching device 15 is connected to outputs of receivers of the means 10 transponder 18 tracking radar and those of beacon 21 tracking radar 20. Depending on the missile position with respect to the PA scanning sector, switching device 15, in response to the j angular misalignment evaluator 14 command, connects this or other receiver to the tracking system of the tracking radar of transponder 18 of means 10.
When a missile reaches the PA beam, pattern of the PA is widened. Device 17 for widening the pattern of the means 10 tracking radar ensures the range lock-on and tracking of a missile, and the radio guidance of the same until the missile enters the PA operation angles sector. The device for widening the pattern of the means 10 transponder tracking radar antenna can be implemented in the form of a plurality of the constant voltage sensors connected to inputs of power amplifiers whose 2J outputs are connected to the control windings of PA phase a changers. Voltage values of said plurality of sensors correspond to the stepwise approximation of parabolical function that is symmetrical relative to the plurality central member.
The above-described arrangement ensures an highly-reliable acquisition of a vertically launched missile and delivery of the same into the PA beam even in a relatively small beam deviation sector when a PA having a small number of members is used.
Signals of derivatives of the tracked targets coordinates from systems 11 for simultaneous tracking basing on four coordinates arrive at input of device 12 for analysing the combat operation result, which device on the basis of a change in the nature of the dependency of the target angular velocities on the time makes a conclusion as to the fact of destruction of a target, and said results are displayed by information display system 22.
Monitoring of serviceability of the entire AAMU guidance system hardware is performed by device 23 coupled to detection means 2, radar-based identification interrogator 4, means 10 for tracking and precision-measurement of the target and missile coordinates, and tracking radar 20 of missile beacon 21 (these interrelationships are not shown in Fig. 1). The results of monitoring of the hardware serviceability are displayed by information display system 22. Use of device 23 provides a continuous monitoring of readiness of the AAMU guidance system hardware and enables an operator to interfere operatively with the operation process, which improves the battle readiness of an AAMU.
'a
Second evaluator 5 for evaluating the time a target enters the lasnch area according to the data obtained from device 3, estimates the time a target enters the launch area and estimates the time when devices 6 for the missile pre-launch preparation and launch execution shall be turned on, which .1 devices send the preparation and launch commands to a missile.
Thus, these estimates are provided as early as before the information on the target coodinates is obtained from output of means 10 for tracking and precision-measurement of the target and missile coordinates.
Said target data (the target coordinates and their derivatives) from output of the range and azimuth tracking device 3 are supplied to the system 11 for simultaneous tracking basing on four coordinates (azimuth, elevation, range and Doppler frequency) of several objects by radar of means 10 for tracking and precision-measurement of target coordinates, ~5 and processed by said means.
The antenna of the radar of means 10 is implemented in the form of a phased array (PA). The tracking is carried out in the time-division mode by consecutive referrals of the PA beam to targets and missiles.
3~ To proceed to the target lock-on by the radar of means 10, without the operator's attendance, programmable radar-based search device 9 arranges for the target search within the space area determined by the target-indicating data errors committed by the all-round looking radar of means 2. Device 9 35 consecutively generates coordinates of the PA angular positions, which are delivered to system 8 for controlling the PA beam. As a result of operation of the controlling system 8, the PA beam is directed to a pre-determined angular direction.
Consecutive positions of the PA pattern can be a field raster, for example.
Radar of means 10, in each angular direction, emits a sounding signal. The echo signal, received by the radar receiver of means 10, is used to detect targets and determine their coordinates. Therefor, used is the joint processing of information obtained from a number of angular directions and the range and speed increments.
The joint processing can be done, for example, on the basis of evaluation of the energy centre (gravity centre of a spatial figure). The so obtained amended targets' coordinates are supplied from the means 10 radar to tracking systems 11 for simultaneous tracking basing on four coordinates. Owing to a sufficient accuracy of determining said target coordinates, the simultaneous four-coordinate tracking systems 11 from this moment on proceed to the continuous automatic target tracking.
Such arrangements for the target search using the means 10 tracking radar within the limit of the target-indicating errors 2~ committed by the all-round looking radar of detection means 2 allow to proceed to the lock-on by the tracking means 10 radar in a short time without the operator's attendance.
The target coordinates from output of the simultaneous tracking system 11 are delivered to input of evaluator 7 for ~5 evaluating the time a target enters the launch area, which s evaluator from that moment on evaluates the amended time a target will enter the launch area and performs the exact estimate of the time the missile pre-launch and launch execution devices 6 shall be turned on.
30 Signals from output of the tracking means 10 radar receiver, as well as the locked-on targets coordinates and their derivatives from the simultaneous tracking systems 11 are supplied to input of identification device 13. The identification device determines the features that characterise 35 the target being tracked. The following can be used as such features, for example: spectral composition of the signal reflected from a target, a signal strength and target movement parameters, such as the velocity vector module and tracked target altitude. Basing on the logical analysis of combinations of the determined features, a decision is made on the target's association with one of the classes. The identification result is given to a unit for generating the control commands of the tracking means 10 transponder 18 to match the time and mode of the missile combat portion explosion with the radio-controlled explosive device activation time, which allows to improve probability that a target will be destroyed.
In the pre-launch period, the target coordinates from output of tracking system 11 are supplied to evaluator 16 for evaluating the pre-launch command information and deviation angles. The signals generated by evaluator 16 are continuously delivered to autopilot 19. The deviation angle signals generated at the launch moment are stored by a storage member of autopilot 19, and at the autonomous flight stage the missile hull is steered by autopilot 19 and the controls such that direction of the longitudinal axis thereof will be proximate to the missile flight kinematic path tangent. When the missile position at the moment the radio guidance commences is such, a short range required to bring a missile to the kinematic path and a short range to the nearest destruction area boundary are ensured. Missiles are launched vertically. Use of the vertical launch allows to increase the carried missiles store owing to ~$ their positioning at the rotation centre, which permits to a decrease the inertia moment and the azimuth drive capacity.
Immediately after the launch, tracking radar 20 of missile beacon 21 performs acquisition and tracking of missile beacon 21 according to the angular coordinates. Employment of beacon 21 in a missile and providing the tracking radar 20 system with said beacon ensures the missile acquisition and tracking at the stage of its autonomous flight when the same is still outside the limits of the PA beam scanning sector of tracking means 10 radar of transponder 18.
At the same time, the phased array of the radar of means 10 forms a wide pattern for transmitting the interrogating signals and receiving the transponder 18 response signals.
g Evaluator 14 for evaluating the angular misalignments compares the missile angular coordinates, as measured by tracking radar 20 of_ missile beacon 21, and the PA scanning sector boundaries.
Angular misalignments evaluator 14 provides the target-indicating data to the means 10 transponder tracking radar from tracking radar 20 of beacon 21 and performs the switching, using switching means 15 of said radar of means 10 to implement lock-on of transponder 18 according to the angular coordinates when a missile enters the phased array sector. Switching device 15 is connected to outputs of receivers of the means 10 transponder 18 tracking radar and those of beacon 21 tracking radar 20. Depending on the missile position with respect to the PA scanning sector, switching device 15, in response to the j angular misalignment evaluator 14 command, connects this or other receiver to the tracking system of the tracking radar of transponder 18 of means 10.
When a missile reaches the PA beam, pattern of the PA is widened. Device 17 for widening the pattern of the means 10 tracking radar ensures the range lock-on and tracking of a missile, and the radio guidance of the same until the missile enters the PA operation angles sector. The device for widening the pattern of the means 10 transponder tracking radar antenna can be implemented in the form of a plurality of the constant voltage sensors connected to inputs of power amplifiers whose 2J outputs are connected to the control windings of PA phase a changers. Voltage values of said plurality of sensors correspond to the stepwise approximation of parabolical function that is symmetrical relative to the plurality central member.
The above-described arrangement ensures an highly-reliable acquisition of a vertically launched missile and delivery of the same into the PA beam even in a relatively small beam deviation sector when a PA having a small number of members is used.
Signals of derivatives of the tracked targets coordinates from systems 11 for simultaneous tracking basing on four coordinates arrive at input of device 12 for analysing the combat operation result, which device on the basis of a change in the nature of the dependency of the target angular velocities on the time makes a conclusion as to the fact of destruction of a target, and said results are displayed by information display system 22.
Monitoring of serviceability of the entire AAMU guidance system hardware is performed by device 23 coupled to detection means 2, radar-based identification interrogator 4, means 10 for tracking and precision-measurement of the target and missile coordinates, and tracking radar 20 of missile beacon 21 (these interrelationships are not shown in Fig. 1). The results of monitoring of the hardware serviceability are displayed by information display system 22. Use of device 23 provides a continuous monitoring of readiness of the AAMU guidance system hardware and enables an operator to interfere operatively with the operation process, which improves the battle readiness of an AAMU.
'a
Claims
1. A guidance system for a short-range anti-aircraft missile unit, comprising mounted on a single self-propelled carrier,or in a conveyance container:
detection means 2 having an all-round looking radar;
radar-based identification interrogator 4;
means 10 for tracking and precision-measurement of the target and missile coordinates;
means 22 for displaying an information;
devices 6 for the missile pre-launch preparation and launch execution;
transponder 18;
missile autopilot 19;
computation control means, including evaluator 7 for evaluating the time a target enters the launch area, and evaluator 14 for evaluating the angle misalignment, characterised in further comprising:
means 1 for partial controlling of antenna beams of the all-round looking radar, having a phase-shift device;
means 3 for the range and azimuth tracking;
system 8 for controlling the beam of a radar of means 10 for tracking and precision-measurement of coordinates, the antenna of which radar is implemented in the form of a phased array;
programmable search device 9;
system 11 for simultaneous tracking basing on four coordinates (azimuth, elevation, range and Doppler frequency) of a number of objects using the radar of means 10 for tracking and precision-measurement of coordinates;
device 17 for controlling the pattern width;
missile beacon 21;
tracking radar 20 of missile beacon 21;
switching device 15;
device 13 for identification of the target class and adapting the modes of operation of the missile control systems, including a signal spectral analysis unit;
evaluator 16 for evaluating the pre-launch command information and missile deviation angles after the vertical launch;
device 12 for analysing the launch results;
and the computation control means further comprises second evaluator 5 for evaluating the time a target enters the launch area;
the pattern of antenna of radar-based identification interrogator 4 being deployed in azimuth relative to the antenna of the all-round looking radar of detection means 2 in the direction opposite to that of rotation of the latter;
a transmitter of the all-round looking radar of detection means 2 being connected to the phase-shift device of means 1 for controlling the antenna beams of the all-round looking radar of detection means 2, which phase-shift device is connected to antenna emitters of the all-round looking radar of detection means 2;
output of a receiving system of the all-round looking radar of detection means 2, which system is of the «n-channel»
type, being coupled to radar-based identification interrogator 4 and to a first input of range and azimuth tracking device 3, a second input of which being connected to output of radar-based identification interrogator 4;
output of range and azimuth tracking device 3 being coupled to second evaluator 5 for evaluating the time a target enters the launch area, and to system 11 for simultaneous tracking basing on four coordinates;
programmable search device 9, via beam control system 8, being connected to antenna of the radar of means 10 for tracking and precision-measurement of coordinates, whose receiver outputs being connected to system 11 for simultaneous tracking basing on four coordinates;
evaluator 16 for evaluating the pre-launch command information and the missile deviation angles, via its input, being connected to system 11 for simultaneous tracking basing on four coordinates, and via its output - to missile autopilot 19;
tracking radar 20 of missile beacon 21 being connected, via device 17 for controlling the pattern width, to antenna of the transponder tracking radar of means 10 for tracking and precision-measurement of coordinates;
switching device 15, via its inputs, being coupled to output of the transponder tracking radar receiver of means 10 for tracking and precision-measurement of coordinates, to tracking radar 20 of beacon 21 and to output of evaluator 14 for evaluating the angle misalignment, and via its output being coupled to the transponder tracking system of means 10 for tracking and precision-measurement of coordinates;
inputs of evaluator 14 for evaluating the angle misalignment being coupled to system 11 for simultaneous tracking basing on four coordinates and to tracking radar 20 of beacon 21;
device 13 for the target class identification and adapting the modes of operation of the missile control systems, via its inputs, being connected to system 11 for simultaneous tracking basing on four coordinates and to the radar receiver of means for tracking and precision-measurement of coordinates, and via its output - to a device for transmitting the control information to missiles, which device belongs to means 10 for tracking and precision-measurement of coordinates;
launch result analysis device 12, via its input, being connected to system 11 for simultaneous tracking basing on four coordinates, and via its output - to information display means 22;
input of evaluator 7 for evaluating the time a target enters the launch area being connected to system 11 for simultaneous tracking basing on four coordinates; and outputs of both evaluators 5 and 7 for evaluating the time a target enters the launch area being connected to devices 6 for the missile pre-start preparation and launch execution.
detection means 2 having an all-round looking radar;
radar-based identification interrogator 4;
means 10 for tracking and precision-measurement of the target and missile coordinates;
means 22 for displaying an information;
devices 6 for the missile pre-launch preparation and launch execution;
transponder 18;
missile autopilot 19;
computation control means, including evaluator 7 for evaluating the time a target enters the launch area, and evaluator 14 for evaluating the angle misalignment, characterised in further comprising:
means 1 for partial controlling of antenna beams of the all-round looking radar, having a phase-shift device;
means 3 for the range and azimuth tracking;
system 8 for controlling the beam of a radar of means 10 for tracking and precision-measurement of coordinates, the antenna of which radar is implemented in the form of a phased array;
programmable search device 9;
system 11 for simultaneous tracking basing on four coordinates (azimuth, elevation, range and Doppler frequency) of a number of objects using the radar of means 10 for tracking and precision-measurement of coordinates;
device 17 for controlling the pattern width;
missile beacon 21;
tracking radar 20 of missile beacon 21;
switching device 15;
device 13 for identification of the target class and adapting the modes of operation of the missile control systems, including a signal spectral analysis unit;
evaluator 16 for evaluating the pre-launch command information and missile deviation angles after the vertical launch;
device 12 for analysing the launch results;
and the computation control means further comprises second evaluator 5 for evaluating the time a target enters the launch area;
the pattern of antenna of radar-based identification interrogator 4 being deployed in azimuth relative to the antenna of the all-round looking radar of detection means 2 in the direction opposite to that of rotation of the latter;
a transmitter of the all-round looking radar of detection means 2 being connected to the phase-shift device of means 1 for controlling the antenna beams of the all-round looking radar of detection means 2, which phase-shift device is connected to antenna emitters of the all-round looking radar of detection means 2;
output of a receiving system of the all-round looking radar of detection means 2, which system is of the «n-channel»
type, being coupled to radar-based identification interrogator 4 and to a first input of range and azimuth tracking device 3, a second input of which being connected to output of radar-based identification interrogator 4;
output of range and azimuth tracking device 3 being coupled to second evaluator 5 for evaluating the time a target enters the launch area, and to system 11 for simultaneous tracking basing on four coordinates;
programmable search device 9, via beam control system 8, being connected to antenna of the radar of means 10 for tracking and precision-measurement of coordinates, whose receiver outputs being connected to system 11 for simultaneous tracking basing on four coordinates;
evaluator 16 for evaluating the pre-launch command information and the missile deviation angles, via its input, being connected to system 11 for simultaneous tracking basing on four coordinates, and via its output - to missile autopilot 19;
tracking radar 20 of missile beacon 21 being connected, via device 17 for controlling the pattern width, to antenna of the transponder tracking radar of means 10 for tracking and precision-measurement of coordinates;
switching device 15, via its inputs, being coupled to output of the transponder tracking radar receiver of means 10 for tracking and precision-measurement of coordinates, to tracking radar 20 of beacon 21 and to output of evaluator 14 for evaluating the angle misalignment, and via its output being coupled to the transponder tracking system of means 10 for tracking and precision-measurement of coordinates;
inputs of evaluator 14 for evaluating the angle misalignment being coupled to system 11 for simultaneous tracking basing on four coordinates and to tracking radar 20 of beacon 21;
device 13 for the target class identification and adapting the modes of operation of the missile control systems, via its inputs, being connected to system 11 for simultaneous tracking basing on four coordinates and to the radar receiver of means for tracking and precision-measurement of coordinates, and via its output - to a device for transmitting the control information to missiles, which device belongs to means 10 for tracking and precision-measurement of coordinates;
launch result analysis device 12, via its input, being connected to system 11 for simultaneous tracking basing on four coordinates, and via its output - to information display means 22;
input of evaluator 7 for evaluating the time a target enters the launch area being connected to system 11 for simultaneous tracking basing on four coordinates; and outputs of both evaluators 5 and 7 for evaluating the time a target enters the launch area being connected to devices 6 for the missile pre-start preparation and launch execution.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EA199900050A EA002202B1 (en) | 1998-10-19 | 1998-10-19 | A guidance system for a short-range anti-aircraft missile unit |
| EA199900050 | 1998-10-19 | ||
| PCT/EA1999/000007 WO2000023819A1 (en) | 1998-10-19 | 1999-09-28 | System for controlling a unit of short-range surface-to-air missiles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2325146A1 true CA2325146A1 (en) | 2000-04-27 |
Family
ID=8161478
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002325146A Abandoned CA2325146A1 (en) | 1998-10-19 | 1999-09-28 | System for controlling a unit of short-range surface-to-air missiles |
Country Status (4)
| Country | Link |
|---|---|
| CA (1) | CA2325146A1 (en) |
| EA (1) | EA002202B1 (en) |
| GR (1) | GR1003436B (en) |
| WO (1) | WO2000023819A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2461843C1 (en) * | 2011-04-29 | 2012-09-20 | Открытое акционерное общество "Федеральный научно-производственный центр "Нижегородский научно-исследовательский институт радиотехники" | Method of processing radar information in network information structure of automated control system |
| CN109583132B (en) * | 2018-12-18 | 2023-04-07 | 中国人民解放军国防科技大学 | Hypersonic aircraft landing probability calculation method based on radar detection error |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1601829A (en) * | 1978-05-08 | 1981-11-04 | Raytheon Co | Vehicle guidance apparatus |
| EP0276530B1 (en) * | 1987-01-28 | 1992-11-11 | Hercules Incorporated | Millimeter wave length guidance system |
| US4665401A (en) * | 1980-10-10 | 1987-05-12 | Sperry Corporation | Millimeter wave length guidance system |
| DE3318340C1 (en) * | 1983-05-20 | 1992-03-05 | Siemens Ag | Procedure for tracking target objects |
| FR2603695B1 (en) * | 1986-09-09 | 1990-10-19 | Thomson Csf | METHOD AND DEVICE FOR VIEWING TARGETS AND / OR TARGET POSITIONS USING MEANS OF ACQUISITION OF WEAPONS SYSTEM |
| NL1004025C2 (en) * | 1996-09-13 | 1998-03-16 | Hollandse Signaalapparaten Bv | Method for determining an impact point of a fired projectile with respect to a target. |
-
1998
- 1998-10-19 EA EA199900050A patent/EA002202B1/en not_active IP Right Cessation
-
1999
- 1999-09-28 CA CA002325146A patent/CA2325146A1/en not_active Abandoned
- 1999-09-28 WO PCT/EA1999/000007 patent/WO2000023819A1/en active Application Filing
- 1999-10-18 GR GR990100359A patent/GR1003436B/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| GR990100359A (en) | 2000-06-30 |
| EA199900050A1 (en) | 2000-04-24 |
| GR1003436B (en) | 2000-09-19 |
| EA002202B1 (en) | 2002-02-28 |
| WO2000023819A1 (en) | 2000-04-27 |
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